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强化传热期刊
影响因子: 0.562 5年影响因子: 0.605 SJR: 0.175 SNIP: 0.361 CiteScore™: 0.33

ISSN 打印: 1065-5131
ISSN 在线: 1026-5511

强化传热期刊

DOI: 10.1615/JEnhHeatTransf.2011003253
pages 419-432

FILM COOLING PERFORMANCE IN A LOW-SPEED 1.5-STAGE TURBINE: EFFECTS OF BLOWING RATIO AND ROTATION

Zhi Tao
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics The Collaborative Innovation Center for Advanced Aero-Engine of China Beihang University Beijing 100191, China
Guoqing Li
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, 100190, China; University of Chinese Academy of Sciences, Beijing, 100190, China
Hongwu Deng
National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beihang University, Beijing, 100191, China
Jun Xiao
National Key Laboratory of Science and Technology on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing, 100191, China
Guoqiang Xu
National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beihang University, Beijing, 100191, China; School of Energy Science and Engineering, Harbin institute of Technology, Harbin, 150001, China
Xiang Luo
National Key Laboratory of Science and Technology on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing, 100191, China

ABSTRACT

This paper presents experimental investigations on film cooling performance under rotation in a low-speed 1.5-stage turbine using the thermochromic liquid crystal (TLC) technique. The experiment was accomplished in a test facility which was recently established to study rotating film cooling performance in realistic turbine stages. Eighteen blades of chord length of0.1243 m and height of 0.099 m were installed in the rotor. A film hole with diameter of 0.004 m, angled 28° and 36° tangentially to the pressure surface and suction surface in streamwise, respectively, was set in the middle span of the rotor blade. All measurements were made at three different rotating speeds of 600, 667, and 702 rpm with the blowing ratios varying from 0.3 to 3.0. The Reynolds number based on the mainstream velocity of the turbine outlet and the chord length of the rotor blade was fixed at 1.89 × 105. Results show that on the pressure side, the film coverage and cooling effectiveness scaled up with the blowing ratio and the film deflected centrifugally; on the suction side, the maximum film coverage and cooling effectiveness were obtained at moderate blowing ratio and a centripetal deflection of the film was observed. The film deflection could be amplified by either decreasing the blowing ratio or increasing the rotation number on both sides. Overall, blowing ratio and rotation play significant roles in the film cooling performance.